Guidance control for missile



Jan. 30, 1962 R. WELLER 3,913,931

GUIDANCE CONTROL FOR MISSILE Filed June 3, 1949 2 Sheets-Sheet 1MECHANISM A/V TENN/1 DEFLECT/NG CHARGE SELEG T/VE TRA NSM/TTER FREQUENCY$0 URGE 23 amen m ROYAL WELLER Jan. 30, 1962 R. WELLER 3,018,981

GUIDANCE CONTROL FOR MISSILE v Filed June 3, 1949 2 Sheets-Sheet 2 W1 AI.

D wm mq E BAND P4 55 F L TERS RECE/ l/ER TRANSMITTER 4 s50 ass: 12556lasso 20.950

ROYAL WELLE I araasr Patented Jan. 30, 1962 3,018,981 GUmANCE CONTROLFOR MISSILE Royal Weller, Silver Spring, Md. (Rochester, N.Y.) FiledJune 3, 1949, Ser. No. 97,061 12 Claims. (Cl. 244-44) (Granted underTitle 35, US. Code (1952), sec. 266) The present invention relates toguided missiles and more particularly to a signal transmitting andreceiving system for performing a control function thereon such,

for example, as a steering operation effective to change I will bedeflected from the original trajectory by a signal 3 l of a selectedfrequency. In other words, all of the launched missiles will becontrollable by a signal of a certain frequency when they have travelleda certain period of time from the time of launching.

An object of the present invention is to provide a new and improvedarrangement for changing the direction of flight of a missile to meet achanged target condition.

Another object is to provide apparatus for changing the course of amissile in flight without influencing other missiles launched before orafter the launching of the instant missile.

Still another object is to provide apparatus for changing the trajectoryof a missile in flight having the qualities of simplicity andruggedness.

Other objects and many of the attendant advantages of this inventionwill be readily appreciated as the same becomes better understood byreference to the following detailed description when considered inconnection with the accompanying drawings, wherein:

FIG. 1 is a diagrammatic side elevation of a missile in accordance withthe present invention, parts being broken away;

FIG. 2 is a diagram of the control circuit therefor and associatedapparatus;

FIG. 3 is a diagram of a signal transmitting apparatus for use with thepresent invention;

FIG. 4 is a diagram of a modified form of the control circuit; and

FIG. 5 is a diagram of a transmitter for use with the missile of FIG. 1.

Referring more particularly to the drawings in which like numeralsindicate like parts throughout the several views there is illustrated inFIG. 1 a missile 10 having a casing composed of a pair of portions 11and 12. The portion 11, in the present instance, is employed as a groundfor the radio receiver of a control mechanism 13 contained therein,while portion 12 serves as the antenna therefor. The portions 11 and 12are suitably insulated from each other in any well-known manner as by aninsulating band 14. An explosive deflecting charge 15 is mounted in oneside of the portion 11 and is arranged to be operated by mechanism 13under conditions to be hereinafter more fully described.

An indicated in FIG. 2 the mechanism 13- comprises a radio receiver 16which is grounded to portion 11 of the casing 10 and has its antennalead connected to portion 12 of the casing. Arranged in the tuningcircuit 17 of receiver 16 is a variable condenser 13 driven by a .clock19, the condenser being arranged to progressively vary its capacityduring the flight of the missile. In this manner the receiver 1-6 willbe tuned to receive a radio signal comprising any one of severalpossible, continually changing frequencies at any point in thetrajectory of the missile. It is to be understood that the clock 19 isprovided with a starter mechanism of any well-known variety which willoperate to start the clock at the instant of launching of the missile10. It will thus be seen that the receiver will be tuned to receive acontrol signal of a certain frequency at only a small fractional orincremental portion of the trajectory and will be tuned to receive aplurality of progressively different frequencies throughout the flightrespectively corresponding to other small fractional portions of thetrajectory. The missile, thus may be controlled at any point in itsflight by a control signal of a frequency which matches the tunedfrequency of the receiver controlled by the instant setting of thevariable condenser and corresponding to the instant position of themissile. It is also apparent that other missiles in flight which werelaunched either before or after the instant missile will not be affectedat this time by the signal for controlling the aforedescribed missile,for-the reason that the control signal is of short duration and thereceivers of the other missiles are tuned at this instant to differentfrequencies corresponding respectively to their positions in theirtrajectories at the time the signal is transmitted.

In order to provide for firing the charge 15 a relay 21 has is operatingcoil 22 in a circuit 23 arranged to be energized at the instant a signalof the proper frequency is received by the radio receiver 16. When coil22 is energized make contact 24 is brought into circuit closing positionagainst contact 25 thus closing a control circuit 30 including a sourceof power BA connected to make contact 24 through contact 25 to anelectroresponsive detonator 26 or other means for firing deflectingcharge 15 and thence to source of power BA.

The particular missile referred to herein is of the spinning type and inaltering the trajectory thereof it is possible to improve the targetimpact probability of the missile whereas no such possibility wouldexist if the target should change course and the missile were restrictedto its initial trajectory.

FIG. 3 illustrates in diagrammatic form a transmitter suitable for usewith the present invention which comprises a transmitter 27 havingassociated therewith a selective frequency source 28 whereby signals ofany desired frequency may be selected and transmitted to the missile atany time during the flight thereof.

A modification of the arrangement for progressively selecting thereceivable signal frequencies during the flight of the missile isillustrated in diagrammatic form in FIG. 4. A clock 29 is provided whichis started as the missile is launched. The clock 29 drives a rotatablebrush contact arm 31 having an elongated brush 32. A plurality ofex-tendable contact rods 33 are arranged in radially spaced relationaround the path of travel of the contact arm 31 and normally spacedtherefrom. The contact rods 33- are yieldably held in their normalposition preferably by means of springs 34. Extensions 35 of contactrods are employed as movable cores for the solenoid coils 36. Aband-pass filter circuit is indicated at 37, it being understood thatthere is included therein a plurality of filters each of which is tunedto a different frequency to control a selected one of the solenoid coils36. A receiver 38 as illustrated in FIG. 4 is provided for the re-'ception of signals as in the preferred form of the invention.

In operation a signal of a selected frequency is received by thereceiver 38. The signal is passed from the "receiver to the band-passfilters 37 wherein the filter tuned .to pass ,the' particular frequencyof the instant signal energizes the solenoid coil connected theretowhich moves the contact rod associated therewith into contact with thebrush 32 of a selected missile. It will thus be seen that brush 32 willbe driven by the clock during the entire time of flight and will beprogressively adjacent each of the different contact rods at certainintervals of time after the launching of the missile and only thosemissiles which are within the incremental portion of their I'GSPCC. tivetrajectories correspondingto the particular frequency transmitted fromthe transmitting station will have their brushes 32 in position to becontacted by the selected contact rods and their steering chargesfired'thereby. The corresponding contact rodsof other missiles whichwere fired from a gun at ditferent'times, operate. in response to thissignal but without effect as their brushes are not in position to becontacted thereby. i When the signal ceases the brushes arerestoredto-their initial positions by their springs 34.

As illustrated in FIG. 5 a transmitter 39 arranged for use with thecontrol mechanism. of FIG. 2 or the modified form of FIG. 4 and includes.a plurality of signal sources 41, 42., 43, 44 and 45, each .of whichistuned to produce a different frequency such, for example, as

20, 30, 40, 50 and 60 kilocycles,.respectively. It is, of course,understood that any number of signal sources and any number of solenoidcoils may;b ejemployed depending on the length of time, of the flight ofthe mis- In the illustrative embodimentof FIG. 5. a plurality ofswitches 46, 47, 48, 49, and 51 respectively are employed to select thedesired frequency, the switches being marked 4, 8, 12, l6 and 20seconds, respectively,. ifidesired, in

sile and the amount of changes; in frequencydesired.

Ofdl t0 assist the operator-in;selectingthe properswitch a for operationof the correcting apparatus ofaat given missile, such markingsindicating the,.-numb.er. -ofelapsed seconds of time after thelaunchingOfi theymissilec at which time the switches are to be operated-,5 '5 zWhen one of the solenoidco'ils is:energized and the contact rod 33associatedtherewith;moves into engage.- ment with brush 32 it will bevseen that a trajectory correcting circuit 52 comprising one ofthecontact rods 33, battery 3A1, detonator 26, contact ann 31, .and brush32 will be energized while the brush is in contact with the extended rod33, thus firing the correcting charge. It will be understood that iftheinstant missile'receives a signal for a certain frequency before orafter the brush 32 is in the corresponding position the circuit '52 willnot be energized, thus only the missile or missiles launched at acertain time will be affected by any one signal.

As indicated in FIG. 4 the contact assemblies are generally indicated bythe letters A, B, C, D and E which in the present instance areinfluenced or operated by signals of 20, 30, 40, 50 and .60 kilocyclesrespectively, to correspond with the signals of the transmitter 39.

It will be apparent from the-foregoing description that there has beenprovided apparatus whereby missiles may be controlled by an operatorselectively at will While the missiles are in flight course thereof tomeet changing positions of the target or for other reasons.

While the invention has been described-with particularity with respectto a projectile, it is not solimited as the term missile as employedherein is intended to include other missile weapons'such, for example,as rockets and bombs and the invention, therefore, is also suitable foruse with spin type rockets, bombs and the like or any other type ofmissile in which it is desired to change the course thereof duringflight. 7

Obviously many modifications and variations of the present invention arepossible in the light ofithe above teachings. It is therefore to beunderstood that within the scope of the appended claims the inventionmay be practiced otherwise than as specifically described.

The invention described herein may be manufactured and used by or forthe Government of the United States of America for governmental purposeswithout the payment of any royalties thereon or therefor.

What is claimed as new and desired to be secured by Letters Patent ofthe United States is:

1. Apparatus for altering the trajectory of a missile comprising, aclock arranged to be started as the missile is launched, a selectormechanism having a brush rotated by said clock and a plurality ofnormally and yieldably retracted radially arranged contact members, saidcontact members being arranged to be contacted when in an extendedposition by the brush member as it rotates, a plurality of actuatingcoils individual to said contact members for moving .the contact membersfrom the retractedto the extended position, a plurality of band-passfilters of different valuesvforvcontrolling the operating frequency ofthe actuating, coils and operatively connectedthereto for energizing aselected coil when a matching frequency is received, anda radio receiverin the missile for receiving said frequencies.

2.. Apparatus for changing the trajectory of a missile in flightcomprising, a transmitter under the control of ano'perator and havingmeans for transmitting signals of different selected fixed frequencies,a receiver in said missile for. receiving said signals, a clockconstructed and arranged to be started as the missile is launched,tuning means continuously driven by said clock for adjusting saidreceiver continuously and progressively to receive a different one ofsaid signals during each of a plurality of successive periods of timeafter the launching of the missile whereby a transmitted signal of aselected frequency. may be received by the receiver only during acertain period of time after the launching of the missile, an explosivesteering charge carried by the missile,and circuitrclosingmeans operatedby said receiver for firing said charge when said' signal of selectedfrequency is receivedduring the period of time when the receiver istuned to receive said frequency.

3. Apparatus for changing the trajectory ofa missile infiightcomprising, a clock in said missile arranged to be started as themissilelis launched, a radio receiver carried by the missile, frequencytuning apparatus driven by saidv clock and operatively connected to saidreceiver for continuously and progressively varying the signal frequencywhich the receiver is adapted to receive whereby the receiver is tunedto receive certain signals, each of a different frequency only atcertain periods of time during the flight of the missile, an explosivesteering charge, and means controlled by said receiver for explodingsaid charge when the receiver receives a signal of a frequency inmatching relation to the period of time during which it is received.

4. In apparatus for changing the trajectory of a missile in flightcomprising, a clock arranged to be started as the missile is launched, avariable condenser continuously driven by said clock and arranged in thetuning circuit of a radio receiver whereby the receivable frequency ofthe receiver is progressively and continuously changed during the flightof the missile, an explosive steering charge, and circuit closing meansoperatively connected to said receiver for exploding said charge whenthe condenser is tuned to the frequency of a transmitted signal.

5. In a missile comprising a casing having a pair of electricallyconducting sections insulated one from the other, a radio receivermounted Within said casing, one of said sections being operativelyconnected to said receiver to provide an antenna therefor, the other ofsaid sections being operatively connected tosaid receiver to provide aground therefor, a clock in said casing arranged to be started as themissile is launched, a tuning mechanism' for the receiver arranged to bedriven continuously by said clock at a predetermined rate and tocontinuously and progressively change the frequency receivable by saidreceiver during the flight of the missile, an-explosive steering chargearranged to exhaust at one side of the casing, and means controlled bysaid receiver for firing said steering charge when the receiver receivesa signal corresponding in frequency to the tuned frequency thereof.

6. An apparatus of the character disclosed for changing the trajectoryof a missile comprising, a radio receiver carried by the missile, meansfor continuously and progressively changing the tuning of said receiverat a predetermined rate while the missile is in flight, means forsetting the tuning means in operation as the missile starts on saidflight, an explosive steering charge carried by the missile and adaptedto exhaust therefrom laterally with respect to the line of flight, andmeans operatively connected to said receiver and controlled thereby forfiring said charge when the receiver receives a radio signal to which itis tuned.

7. In a system for altering the course of a projectile, in combination,a transmitting station having means for transmitting radio signalsselectively of different fixed frequencies, each of said signals havinga frequency corresponding to a different incremental fractional portionof the trajectory of the projectile, a radio receiver carried by saidprojectile, means for continuously and progressively changing the tuningof said receiver at a predetermined fixed rate during the flight of theprojectile whereby the receiver is responsive to a selected signal fromsaid transmitting station during a selected portion of said trajectorycorresponding thereto, an explosive steering charge carried by theprojectile and arranged to exhaust from one side thereof as the chargeis fired, and means including an elect-ro-responsive detonatoroperatively connected to said receiver and controlled thereby forexploding said charge as a signal is received by the receiver.

8. In a system of the character disclosed for changing the trajectory ofa missile in flight, in combination, a source of radio signals of fixedfrequency at a control station, means for initiating radio transmissionof said signals at a predetermined interval of time after the projectilehas been fired from a gun, radio receiving means on the projectile,means carried by the projectile for continuously and progressivelychanging the tuning of said receiver at a rate proportional to thedistance traveled by the projectile during flight thereby to maintaincorrelative relation between the instant position of the projectile andthe signal frequency received by said receiver, an explosive deflectingcharge carried by the projectile and adapted to exhaust radially in onedirection from the axis thereof, and means including anelectroresponsive detonator controlled by said receiver for explodingsaid charge when a signal is received from the control stationcorresponding to the instant frequency of the receiver to which thereceiver is tuned.

9. In a system for selecting a missile from a group of missiles inflight and fired from a gun in successive order, in combination, aplurality of tuned radio receivers respectively carried by the missiles,means on each missile for continuously and progressively changing thetuning of the receiver during the flight of the missile, means at acontrol station for suddenly transmitting a radio signal correspondingin frequency to the instant tuned frequency of a missile to be selected,an explosive steering charge on each of the missiles, and means forfiring said charge as a signal is received by the receiver.

10. A radio controlled missile of the character dis closed comprising atuned radio receiver, a control circuit connected to said receiver andrendered effective as a signal is received by the receiver, and meansfor continuously and progressively changing the tuning of the receiverduring flight of the missile whereby the missile is controlled by aradio signal matching in frequency the instant tuned frequency of thereceiver.

11. A claim according to claim 10 and including means for initiatingoperation of the tuning means at the instant the missile is in flight.

12. A Selective system for the remote control of missiles in flight,each of said missiles having a tuned radio receiver carried thereby,means for changing the tuning of said receiver continuously andprogressively at a predetermined rate during said flight, a controlcircuit operatively connected to said receiver and rendered effective asa signal is received by the receiver, means for setting said tuningmeans in operation as the flight is started, and means at a controlstation for transmitting a radio impulse signal of a frequencycorresponding to the instant tuned frequency of one of said receiverswhereby the missile carrying said one of the receivers is selected forcontrol from a plurality of said missiles launched in flight insuccessive order.

References Cited in the file of this patent UNITED STATES PATENTS2,444,750 Ptacek July 6, 1943 2,415,348 Haigney Feb. 4, 1947 2,446,279Hammond Aug. 3, 1948 2,490,844 Sorensen Dec. 13, 1949 2,520,433 RobinsonAug. 29, 1950 2,557,949 Deloraine June 26, 1951

